Table 1 Results of mission design.
Intermediate NEA | 2017 HF |
|---|---|
Mass of Spacecraft (Dry mass + Propellant mass) | 8 t (4 t + 4 t) |
Specific Impulse of SEP | 3,000 s |
Max Thrust of SEP | 1.5 N |
Earth Escape Date | Oct. 7, 2021 |
C3 | 0 km2/s2 |
“Earth-2017 HF” Flight time | 810 days |
“Earth-2017 HF” Propellant Cost | 2.01 t |
Asteroid Arrival Date | Dec. 26, 2023 |
Rendezvous & Assembling Time | 257 days |
Asteroid Escape Date | Sep. 8, 2024 |
“2017 HF-Apophis” Flight Time | 380 days |
“2017 HF-Apophis” Propellant Cost | 0.97 t |
Impact Date | Sep. 23, 2025 |
Mass of the Impactor (Rocks + Spacecraft) | 205.02 t (including 200 t of rocks) |
Impact Relative Velocity | 11.84 km/s |
∆v of Apophis | 39.81 mm/s |
∆ Perigee of Apophis in 2029 | +1,866.93 km |
